CA2305927A1 - Universal joint-type vectoring turbojet exhaust nozzle - Google Patents

Universal joint-type vectoring turbojet exhaust nozzle Download PDF

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Publication number
CA2305927A1
CA2305927A1 CA002305927A CA2305927A CA2305927A1 CA 2305927 A1 CA2305927 A1 CA 2305927A1 CA 002305927 A CA002305927 A CA 002305927A CA 2305927 A CA2305927 A CA 2305927A CA 2305927 A1 CA2305927 A1 CA 2305927A1
Authority
CA
Canada
Prior art keywords
flaps
universal joint
orientable structure
exhaust nozzle
type
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CA002305927A
Other languages
French (fr)
Other versions
CA2305927C (en
Inventor
Didier Georges Feder
Guy Jean-Louis Lapergue
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA Moteurs SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Publication of CA2305927A1 publication Critical patent/CA2305927A1/en
Application granted granted Critical
Publication of CA2305927C publication Critical patent/CA2305927C/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • F02K1/1292—Varying effective area of jet pipe or nozzle by means of pivoted flaps of three series of flaps, the upstream series having its flaps hinged at their upstream ends on a fixed structure, the internal downstream series having its flaps hinged at their upstream ends on the downstream ends of the flaps of the upstream series and at their downstream ends on the downstream ends of the flaps of the external downstream series hinged at their upstream ends on a substantially axially movable structure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/002—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector
    • F02K1/008—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector in any rearward direction

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Joints Allowing Movement (AREA)
  • Exhaust Silencers (AREA)
  • Control Of Turbines (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Details Or Accessories Of Spraying Plant Or Apparatus (AREA)
  • Catching Or Destruction (AREA)

Abstract

L'invention concerne une tuyère d'éjection de turboréacteur axisymétrique et à orientation globale, du type comportant une structure orientable (12) portant une pluralité de volets convergents (21). La structure orientable est montée sur l'extrémité aval d'un carter d'éjection (2) au moyen d'un anneau intermédiaire (9) susceptible de pivoter autour d'un premier axe par rapport au carter d'éjection (2) et de pivoter autour d'un deuxième axe perpendiculaire au premier axe par rapport à la structure orientable (12). Les volets convergents (21) sont articulés à l'extrémité aval de la structure orientable (12). Un anneau de commande unique (27), actionné par trois vérins (28) et relié aux volets convergents (21) par des bielles (24) commande le basculement de la structure orientable (8) et la cinématique des volets (21).The invention relates to an axisymmetric and generally oriented turbojet jet nozzle of the type comprising an orientable structure (12) carrying a plurality of convergent flaps (21). The orientable structure is mounted on the downstream end of an ejection casing (2) by means of an intermediate ring (9) capable of pivoting about a first axis relative to the ejection casing (2) and pivot about a second axis perpendicular to the first axis with respect to the orientable structure (12). The converging flaps (21) are articulated at the downstream end of the orientable structure (12). A single control ring (27), actuated by three jacks (28) and connected to the converging flaps (21) by connecting rods (24) controls the tilting of the orientable structure (8) and the kinematics of the flaps (21).

CA002305927A 1999-04-19 2000-04-14 Universal joint-type vectoring turbojet exhaust nozzle Expired - Lifetime CA2305927C (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR99.04871 1999-04-19
FR9904871A FR2792368B1 (en) 1999-04-19 1999-04-19 TURBOJECTOR EJECTION NOZZLE WITH CARDAN-TYPE ORIENTATION SYSTEM

Publications (2)

Publication Number Publication Date
CA2305927A1 true CA2305927A1 (en) 2000-10-19
CA2305927C CA2305927C (en) 2008-01-08

Family

ID=9544558

Family Applications (1)

Application Number Title Priority Date Filing Date
CA002305927A Expired - Lifetime CA2305927C (en) 1999-04-19 2000-04-14 Universal joint-type vectoring turbojet exhaust nozzle

Country Status (7)

Country Link
US (1) US6327846B1 (en)
EP (1) EP1046806B1 (en)
JP (1) JP4098946B2 (en)
CA (1) CA2305927C (en)
DE (1) DE60013678T2 (en)
ES (1) ES2225041T3 (en)
FR (1) FR2792368B1 (en)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6622472B2 (en) * 2001-10-17 2003-09-23 Gateway Space Transport, Inc. Apparatus and method for thrust vector control
WO2008045062A1 (en) * 2006-10-12 2008-04-17 United Technologies Corporation Fan variable area nozzle for a gas turbine engine fan nacelle with sliding actuation system
RU2455513C1 (en) * 2010-12-02 2012-07-10 Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") Jet nozzle with controlled thrust vector for jet turbine engine
CN103696874B (en) * 2013-12-04 2016-06-01 中国航空工业集团公司沈阳发动机设计研究所 A kind of axisymmetric vectoring exhaust nozzle investigation mission outside the city or town nodal plate
CN103696878B (en) * 2013-12-04 2016-06-22 中国航空工业集团公司沈阳发动机设计研究所 A kind of axial symmetry is received and is expanded jet pipe
CN104033274B (en) * 2014-05-18 2016-08-24 中国航空工业集团公司沈阳发动机设计研究所 The axial symmetry of a kind of single actuating system is received and is expanded jet pipe
US10081091B2 (en) * 2015-06-12 2018-09-25 Postech Academy-Industry Foundation Nozzle, device, and method for high-speed generation of uniform nanoparticles
CN106347637B (en) * 2016-09-29 2018-09-07 湖北航天技术研究院总体设计所 The anti-thermally induced flow integrated apparatus of attitude control jet pipe under a kind of high Mach environment
US11697506B2 (en) * 2020-05-15 2023-07-11 General Electric Company Methods and apparatus for gas turbine bending isolation
CN112761810B (en) * 2021-01-15 2021-10-22 中国航发沈阳发动机研究所 Aero-engine spray pipe and expansion piece pull rod structure thereof
CN113107706B (en) * 2021-04-25 2022-03-22 中国航发沈阳发动机研究所 Binary vector spray pipe outer cover structure and design method thereof
CN115163328B (en) * 2022-04-24 2023-01-17 中国航发四川燃气涡轮研究院 Improved external adjusting structure for binary vector spray pipe

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3003312A (en) * 1957-08-19 1961-10-10 Thompson Ramo Wooldridge Inc Exhaust nozzle for jet engines
FR2470253A1 (en) 1979-11-23 1981-05-29 Snecma ORIENTABLE TUYERE FOR REACTION PROPELLER
FR2501786A1 (en) * 1981-03-13 1982-09-17 Snecma DEVICE FOR BEARING AND GUIDING AN ORIENTABLE NOZZLE OF A REACTION PROPELLER
US4984741A (en) 1987-02-26 1991-01-15 Rolls-Royce Inc. Vectorable variable flow area propulsion nozzle
US4836451A (en) * 1987-09-10 1989-06-06 United Technologies Corporation Yaw and pitch convergent-divergent thrust vectoring nozzle
US4993641A (en) * 1989-10-26 1991-02-19 United Technologies Corporation Gas turbine spherical exhaust nozzle
US5239815A (en) * 1991-09-23 1993-08-31 United Technologies Corporation Sync-ring assembly for a gas turbine engine exhaust nozzle
US5351888A (en) * 1993-05-14 1994-10-04 General Electric Company Multi-axis vectorable exhaust nozzle
US5370312A (en) * 1993-07-13 1994-12-06 United Technologies Corporation Gas turbine engine exhaust nozzle
US5511376A (en) * 1993-08-31 1996-04-30 United Technologies Corporation Axisymmetric vectoring nozzle
ES2105929B1 (en) * 1993-11-23 1998-05-01 Sener Ing & Sist ADJUSTABLE AXISIMETRIC NOZZLE OF VARIABLE GEOMETRY FOR GAS TURBINE PROPELLERS.
ES2136475B1 (en) * 1994-05-20 2000-05-16 Sener Ing & Sist IMPROVEMENTS IN VARIABLE GEOMETRY AXISIMETRIC NOZZLES AND FLOW ORIENTATION INTENDED FOR GAS TURBINE PROPELLERS.

Also Published As

Publication number Publication date
DE60013678T2 (en) 2005-09-29
JP4098946B2 (en) 2008-06-11
EP1046806A1 (en) 2000-10-25
FR2792368B1 (en) 2001-05-25
DE60013678D1 (en) 2004-10-21
ES2225041T3 (en) 2005-03-16
FR2792368A1 (en) 2000-10-20
EP1046806B1 (en) 2004-09-15
US6327846B1 (en) 2001-12-11
CA2305927C (en) 2008-01-08
JP2000320403A (en) 2000-11-21

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MKEX Expiry

Effective date: 20200414